EP4053381A1 - Ringsegmentvorrichtung für turbinenleitschaufeln eines kraftwerks und entsprechende gasturbinenanlage für kraftwerk - Google Patents

Ringsegmentvorrichtung für turbinenleitschaufeln eines kraftwerks und entsprechende gasturbinenanlage für kraftwerk Download PDF

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Publication number
EP4053381A1
EP4053381A1 EP21425007.8A EP21425007A EP4053381A1 EP 4053381 A1 EP4053381 A1 EP 4053381A1 EP 21425007 A EP21425007 A EP 21425007A EP 4053381 A1 EP4053381 A1 EP 4053381A1
Authority
EP
European Patent Office
Prior art keywords
ring segment
turbine
damping pin
gas turbine
damping
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
EP21425007.8A
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English (en)
French (fr)
Inventor
Gabriele Gardella
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Ansaldo Energia SpA
Original Assignee
Ansaldo Energia SpA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Ansaldo Energia SpA filed Critical Ansaldo Energia SpA
Priority to EP21425007.8A priority Critical patent/EP4053381A1/de
Priority to CN202210191455.0A priority patent/CN114991882A/zh
Publication of EP4053381A1 publication Critical patent/EP4053381A1/de
Pending legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04—Antivibration arrangements
    • F01D25/06—Antivibration arrangements for preventing blade vibration
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/28—Arrangement of seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/31—Retaining bolts or nuts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/38—Retaining components in desired mutual position by a spring, i.e. spring loaded or biased towards a certain position
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/84—Redundancy
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise

Definitions

  • the technical field of the present invention relates to the turbomachine assemblies for power plants, i.e. a power plant comprising at least a turbine assembly. More in detail, the present invention refers to the technical field of the gas turbine assemblies for power plants. In this technical field, the present invention refers to the technical problem of how to improve the so called “stator ring” (also known as “sealing ring”).
  • This stator ring is a ring structure formed by a plurality of ring segments centered in the turbine axis and configured for connecting as a ring the inner free ends of the turbine vanes in order to increase the performance, efficiency and lifetime of the system.
  • a gas turbine assembly for power plants comprises a compressor assembly, a combustor assembly and a turbine assembly.
  • the compressor assembly is configured for compressing incoming air supplied at a compressor inlet.
  • the compressed air leaving the compressor assembly flows into a closed volume (called "plenum") and from there into the combustor assembly.
  • This combustor assembly comprises usually a plurality of burners configured for injecting fuel (at least one type of fuel) into the compressed air flow.
  • the mixture of fuel and compressed air enters a combustion chamber where this mixture ignites.
  • the resulting hot gas flow leaves the combustion chamber and flows by the turbine assembly performing a rotating work on a rotor connected to a generator.
  • the same rotor supports also the compressor assembly and it defines the main axis of the system.
  • the turbine assembly comprises a plurality of stages, or rows, of rotating blades that are interposed by a plurality of stages, or rows, of stator vanes.
  • the rotating blades are supported by the rotor whereas the stator vanes are supported by a casing (called “vane carrier”) that is concentric and surrounding the turbine assembly.
  • the hot gas flow has to have a very high turbine inlet temperature.
  • this high temperature involves an undesired high NOx emission level.
  • a so called “sequential" gas turbine is particularly suitable.
  • a sequential gas turbine performs two combustion stages in series.
  • the gas turbine comprises a first combustor and the second combustor that are annular shaped and are physically separated by a turbine, called high pressure turbine. Downstream the second combustor a second turbine unit is present (called low pressure turbine).
  • the gas turbine is not provided with the high-pressure turbine and the combustor assembly is realized in form of a plurality of can-combustors wherein each can-combustor comprises a first combustor and a second combustor arranged directly one downstream the other inside a common casing can-shaped.
  • the terms “circumferential, radial, axial, outer and inner” will refer to the rotor or turbine axis (that is parallel to the main air/hot gas flow).
  • the terms “downstream and upstream” will refer to the main direction of the air/hot gas flow.
  • the turbine assembly comprises a plurality of stages, or rows, of stator vanes wherein in each row is defined by a plurality of vanes arranged adjacent to each other along the circumferential direction.
  • Each vane comprises a body substantially radially shaped extending between an outer end supported by the outer casing and an inner free end facing (and in proximity to) the rotor.
  • each vane in particular the corresponding free end
  • each vane row may vibrate or oscillate during the use of the system.
  • a so called "stator ring” that is an assembly ring-shaped configured for connecting to each other the free ends of a vane row.
  • EP2984295 discloses an example of a stator ring formed by a plurality of ring segments circumferentially coupled to each other. Due to the vane vibration and the different thermal expansions between the vane and the corresponding stator ring segment, the coupling between the vane and the ring segment may wear out and consequently this coupling may become not stable.
  • each pressure bolt is a pushing device configured for being housed in a ring segment and for acting against the vane by means of a restoring force generated by a compressed spring supported by the bolt itself. In this way the vibrations of the vane and the different thermal expansions between vane and corresponding ring segment are dumped avoiding coupling instability.
  • the scope of the present invention is to improve the disclosure of EP2984295 , i.e. to provide an improved stator ring segment comprising a plurality of the pressure bolts or damping pins.
  • a primary scope of the present invention is to provide a new and inventive ring segment device for turbine vanes, i.e. a device configured for being coupled to one or more free ends of vanes and for realizing, cooperating with adjacent segments, a stator ring structure around the axis of the turbine in proximity of the rotor.
  • the starting point of the present invention is to provide a ring segment device comprising:
  • the ring segment device moreover comprises:
  • the pushing force generated by the damping pin devices against the turbine vanes is not locally concentrated (as in EP2984295 ) but distributed along the bar.
  • any local wear of the vane platform at the damping pin devices is avoided and the coupling stability improved.
  • each ring segment device the bar and the ring segment have substantially the same circumferential extent so that for each segment a single bar is present acting to one or more vanes.
  • each vane is provided a damping pin device and each hole housing the corresponding damping pin device has an axis configured so that, in use, each damping pin device is axially arranged in order to better damp the axial vibrations of the free ends of the vanes.
  • each hole housing the corresponding damping pin device is a passing hole comprising a first end obtained in an upstream face of the ring segment and a second end housing a portion of the bar. Consequently, each damping pin device comprises a cylindrical base configured for being coupled (preferably by a screwing coupling) to the first end of the corresponding hole and a head acting in a sprung manner against the bar.
  • Each damping pin device moreover comprises:
  • the sliding coupling between the piston and the head is performed, for instance, by a pin fixed to head protruding inside a slotted hole obtained in the piston.
  • a safety lock device is provided for each damping pin device configured for acting against the base of the corresponding damping pin device.
  • the safety lock device may comprise a pin housed in an inclined hole obtained in the upstream face of the ring segment and acting against a V shaped circumferential slot obtained in the base of the damping pin device.
  • a mounting device configured for coupling the ring segment to a turbine vane before the activation of the damping pin devices.
  • This mounting device may comprise a radial pin housed in a hole obtained in the inner face of the ring segment and having a protruding free end configured for entering a seat obtaining in the turbine vane.
  • This mounting device moreover comprises a screw for fixing in position the radial pin that is accessible by the upstream face of the segment (as the inclined safety lock device and the axial damping pin devices).
  • a gas turbine assembly is an assembly having an axis and comprising:
  • a plurality of ring segment devices of the present invention may be used for forming a stator ring connecting the free ends of a row or stage of turbine vanes.
  • the combustor sector may comprise a plurality of can combustors, wherein each can combustor houses in series a first and a second burner.
  • the gas turbine assembly may comprise in series a first burner, a high pressure turbine, a second burner and a low pressure turbine.
  • this gas turbine assembly 34 for power plants comprises a compressor assembly 35, a combustor assembly 36 and a turbine assembly 37.
  • the compressor assembly is configured for compressing incoming air supplied at a compressor inlet.
  • the compressed air leaving the compressor assembly 35 flows into the combustor assembly 36.
  • This combustor assembly 36 comprises usually a plurality of burners configured for injecting fuel (at least one type of fuel) into the compressed air flow.
  • the mixture of fuel and compressed air enters a combustion chamber where this mixture ignites.
  • the resulting hot gas flow leaves the combustor assembly 36 and enters the turbine assembly 37 performing a rotating work on a rotor 38 having an axis A and connected to a generator 39.
  • Figure 2 discloses a first non-limiting detailed example of a gas turbine assembly for power plant 1 that can be provided with a plurality of new ring segment devices according to the present invention.
  • this gas turbine is a so called "sequential-combustion gas turbine" provided with a high-pressure and a low-pressure turbine.
  • the gas turbine 1 of figure 2 comprises a compressor 3, a first combustor 31, a high-pressure turbine 5, a second combustor 32 and a low-pressure turbine 7.
  • the compressor 3 and the two turbines 5, 7 are integral of or are connected to a common rotor 8 rotating about an axis 9 and surrounded by a concentric casing 10.
  • the compressor 3 is supplied with air and has rotating blades 18 and stator vanes 19 configured to compress the air entering the compressor 3. Exiting the compressor, the compressed air flows into a plenum 11 and from there into a plurality of first burners 12 of the first combustor 31 arranged in a circular pattern around the axis 9.
  • Each first burner 12 is configured for injecting at least one type of fuel (connected to at least one first fuel supply 13) into the compressed airflow.
  • this first burner 12 may be defined as a "premix" burner because is configured for mixing the compressed air and the injected fuel before the ignition.
  • the fuel/compressed air mixture flows into a first combustion chamber 4 annularly shaped, where this mixture ignites.
  • this mixture is initially ignited by an ignitor, for instance by a spark igniter; once ignited the ignition is self-sustaining and the ignitor is turned off.
  • the resulting hot gas leaves the first combustor chamber 4 and is partially expanded in the high-pressure turbine 5 performing work on the rotor 8.
  • Downstream of the high-pressure turbine 5 the partially-expanded hot gas flows into a row of second burners 33 where at least one type of fuel is injected by fuel lances 14 (each burner has one lance).
  • the partially-expanded gas has a high temperature and contains sufficient oxygen for further combustion that occurs by self-ignition in the second combustion chamber 6 arranged downstream of the row second burners 33.
  • These second burners 33 are also called "reheat" burners.
  • the reheated hot gas leaves the second combustion chamber 6 and flows in the low-pressure turbine 7 where it is expanded performing work on the rotor 8.
  • The. low-pressure turbine 7 comprises numerous stages: rows of rotor blades 15 arranged in series in the main flow direction. Such rows of blades 15 are interposed by rows of stator vanes 16.
  • the rotor blades 15 are connected to the rotor 8 whereas the stator vanes 16 are connected to a vane carrier 17 that is a concentric casing surrounding the low-pressure turbine 7.
  • FIG. 3 is a schematic view of a second not-limiting example of a gas turbine that can be provided with a plurality of ring segment device according to the present invention.
  • this gas turbine 20 is a "sequential-combustion gas turbine” that can be provided with the innovative features according to the present invention.
  • figure 3 discloses a partial view of a gas turbine 20 with a compressor 29, a turbine 21 and a sequential combustor 22.
  • the sequential combustor 22 of figure 3 comprises a plurality of so-called can combustors, i.e. a plurality bolt-on can structures wherein each can combustor is provided with first burners 24, a first combustion chamber 25, second burners 26 and a second combustion chamber 27.
  • an mixer may be provided for adding air into the hot gas leaving the first combustion chamber 25 and creating turbulence in the air/hot gas mixture.
  • the hot gas leaves the second combustion chamber 27 it then expands in the turbine 21 performing work on a rotor 30.
  • FIG. 4 discloses a front view (i.e. a view along the hot gas flow direction) of a plurality of ring segment devices of the present invention forming a stator ring connecting the free ends of a row or stage of vanes.
  • the reference A' refers to the axial direction (i.e. parallel to the axis A of the rotor), the reference R the radial direction and the reference C the circumferential direction.
  • figure 4 discloses a stator ring 40 formed by a plurality of ring segment devices 41 adjacent to each other along the circumferential direction C connecting as a single ring the free inner ends of a row of vanes.
  • the reference 42 refer to the row in general and the reference 43 to each single vane.
  • Figure 5 is an enlarged view of a portion of figure 4 disclosing a portion of a single ring segment device 41 according to the present invention.
  • the single ring segment device 41 comprises a ring segment 46 as main body provided with an outer face 44 configured, i.e. shaped, for being coupled to the inner face of one or more vane platforms 45.
  • the shape of each platform 45 and the corresponding shape of the outer face 44 of the ring segment 46 may vary; in this example the coupling is performed by hook portions of the vanes (upstream oriented) housed in corresponding seats obtained in the ring segment 46.
  • This ring segment 46 moreover comprises an upstream face 47 (substantially radial) and an inner face 48 (substantially axial) facing the rotor.
  • Each ring segment 46 comprises a lateral lip 49 configured to be housed in a corresponding lateral seat of the adjacent ring segment 46 for forming a single circumferential ring.
  • the reference 50 refer to a second body of the ring segment device 41 of the present invention, i.e. a circumferential bar that act as an intermediate body between the ring segment 41 and the platform 45.
  • the bar 50 is single bar having a circumferential extent substantially equal to the corresponding segment 46 and it is downstream arranged, i.e. it acts against the downstream hook 51 of the platform 45.
  • References 52, 53 and 54 reported in figure 5 refer to components of the ring device 41 that will be described in detail in the following figures, namely damping pins 52, locking devices 53 and mounting device 54.
  • each damping pin device 52 has an axis A" (in use parallel to the axial direction A) and it is configured for being housed in a corresponding axial hole 55 obtained in the upstream face 47. Consequently, each damping pin device 52 comprises a cylindrical base 53 configured for being coupled (preferably by a screwing coupling) to the first end 54 of the corresponding hole 55.
  • Each damping pin device 52 moreover comprises:
  • the sliding coupling between the piston 57 and the head 56 is performed, for instance, by a pin 59 integral with respect to head 56 and protruding inside a slotted hole 60 obtained in the piston 57.
  • the reference 61 in figure 6 refer to holes configured for housing the ends of a fork tool for screwing the damping pin 52 in the corresponding hole 55.
  • Figures 8 and 9 disclose two different configurations of the damping pin 52 in a ring segment device 41.
  • figure 8 discloses a first step of the activation procedure wherein the base 53 is only in part screwed in the first portion 54 of the hole 55 and, therefore, the spring device 58 is not fully compressed.
  • Figure 9 discloses the configuration of the segment ring device 52 when the base 53 is fully screwed in the first portion 54 of the hole 55 and the spring 58 is thus compressed for generating via the head 56 the required sprung force against the bar 50.
  • Figures 10 and 11 disclose two additional devices of the ring segment device 52 of the present invention.
  • figure 10 discloses a safety lock device that is provided for locking in position a corresponding damping pin device 52.
  • the safety lock device comprises a pin 63 housed in an inclined hole 64 obtained in the ring segment 46 and acting against a V shaped circumferential slot 65 of the base 53 of the damping pin device 52.
  • Figure 11 discloses a mounting device configured for coupling the ring segment 46 to a turbine vane platform 45 before the activation of the damping pin devices 52.
  • the mounting device comprises a radial pin 66 housed in a radial hole 67 of the ring segment 46 and having a protruding free 68 configured for enter a seat 69 obtaining in a turbine vane platform 45.
  • the mounting device moreover comprising an axial screw 70 for fixing in position the radial pin 69.
EP21425007.8A 2021-03-01 2021-03-01 Ringsegmentvorrichtung für turbinenleitschaufeln eines kraftwerks und entsprechende gasturbinenanlage für kraftwerk Pending EP4053381A1 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP21425007.8A EP4053381A1 (de) 2021-03-01 2021-03-01 Ringsegmentvorrichtung für turbinenleitschaufeln eines kraftwerks und entsprechende gasturbinenanlage für kraftwerk
CN202210191455.0A CN114991882A (zh) 2021-03-01 2022-03-01 环节段装置和包括多个这样的环节段装置的燃气涡轮组件

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP21425007.8A EP4053381A1 (de) 2021-03-01 2021-03-01 Ringsegmentvorrichtung für turbinenleitschaufeln eines kraftwerks und entsprechende gasturbinenanlage für kraftwerk

Publications (1)

Publication Number Publication Date
EP4053381A1 true EP4053381A1 (de) 2022-09-07

Family

ID=75426552

Family Applications (1)

Application Number Title Priority Date Filing Date
EP21425007.8A Pending EP4053381A1 (de) 2021-03-01 2021-03-01 Ringsegmentvorrichtung für turbinenleitschaufeln eines kraftwerks und entsprechende gasturbinenanlage für kraftwerk

Country Status (2)

Country Link
EP (1) EP4053381A1 (de)
CN (1) CN114991882A (de)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2004011434A (ja) * 2002-06-03 2004-01-15 Mitsubishi Heavy Ind Ltd 流体機器
JP2010151044A (ja) * 2008-12-25 2010-07-08 Mitsubishi Heavy Ind Ltd タービン翼およびガスタービン
EP2984295A1 (de) 2013-06-28 2016-02-17 Siemens Aktiengesellschaft Dichtringsegment für einen stator einer turbine
EP3054169A1 (de) * 2008-12-25 2016-08-10 Mitsubishi Hitachi Power Systems, Ltd. Statorschaufel-anordnung und gasturbine
FR3056636A1 (fr) * 2016-09-27 2018-03-30 Safran Aircraft Engines Ensemble d'anneau de turbine sans jeu de montage a froid

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2004011434A (ja) * 2002-06-03 2004-01-15 Mitsubishi Heavy Ind Ltd 流体機器
JP2010151044A (ja) * 2008-12-25 2010-07-08 Mitsubishi Heavy Ind Ltd タービン翼およびガスタービン
EP3054169A1 (de) * 2008-12-25 2016-08-10 Mitsubishi Hitachi Power Systems, Ltd. Statorschaufel-anordnung und gasturbine
EP2984295A1 (de) 2013-06-28 2016-02-17 Siemens Aktiengesellschaft Dichtringsegment für einen stator einer turbine
US20160208630A1 (en) * 2013-06-28 2016-07-21 Siemens Aktiengesellschaft Sealing ring segment for a stator of a turbine
FR3056636A1 (fr) * 2016-09-27 2018-03-30 Safran Aircraft Engines Ensemble d'anneau de turbine sans jeu de montage a froid

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